CN103171757B - A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material - Google Patents
A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material Download PDFInfo
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- CN103171757B CN103171757B CN201310126929.4A CN201310126929A CN103171757B CN 103171757 B CN103171757 B CN 103171757B CN 201310126929 A CN201310126929 A CN 201310126929A CN 103171757 B CN103171757 B CN 103171757B
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- 239000002131 composite material Substances 0.000 title claims abstract description 50
- 239000000835 fiber Substances 0.000 title claims abstract description 49
- 230000006978 adaptation Effects 0.000 title claims abstract description 9
- 239000000758 substrate Substances 0.000 claims abstract description 35
- BCAARMUWIRURQS-UHFFFAOYSA-N dicalcium;oxocalcium;silicate Chemical compound [Ca+2].[Ca+2].[Ca]=O.[O-][Si]([O-])([O-])[O-] BCAARMUWIRURQS-UHFFFAOYSA-N 0.000 claims abstract description 4
- 239000003822 epoxy resin Substances 0.000 claims abstract description 4
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 4
- 239000004744 fabric Substances 0.000 claims description 2
- 239000002023 wood Substances 0.000 claims 1
- 230000001141 propulsive effect Effects 0.000 abstract description 3
- 230000008901 benefit Effects 0.000 abstract description 2
- 230000004044 response Effects 0.000 abstract description 2
- 230000003044 adaptive effect Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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Abstract
The invention provides a kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material, belong to trailing edge technical field of driving.Piezoelectric fibre composite material of the present invention is pasted onto on the surface of both sides up and down of substrate.Described piezoelectric fibre composite material is that array is pasted onto on substrate, and alite paste used is epoxy resin.Described piezoelectric fibre composite material connects an independently high tension supply separately, and the output area of high tension supply is-500V ~+1500V.The high tension supply that each piezoelectric fibre composite material of the present invention uses is separate, output voltage does not interfere with each other, therefore the propulsive effort of each piezoelectric fibre composite material output is separate, the distortion of substrate generation variform can be driven, the present invention is installed to alternative conventional rudder face on wing and controls the state of flight of aircraft.Present invention utilizes piezoelectric fibre composite material fast response time, lightweight, be easy to control advantage, the distortion of the variform of substrate generation continuous and derivable can be driven.
Description
Technical field
The present invention relates to a kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material, belong to trailing edge technical field of driving.
Background technology
So far, the aeroperformance how improving aircraft is one of important content of studying of aircraft designer always in aircraft invention.The wing of current fixed wing machine is all outwards stretch from fuselage according to fixing angle, enough firm, large movement or distortion can not be produced during flight, although it has these pneumatic operation parts of front and rear edges wing flap for improving flight efficiency, but itself remains rigid surface, be difficult to the feature according to mission requirements change wing during flight, the pneumatic efficiency of aircraft wing can not get optimization.Address this problem, need to use for reference bionic theory, further investigate from deformation principle, therefore there has been proposed the concept of so-called flexible variant aircraft.
United States Air Force was just classified as adaptive structure technology as far back as 1985 and ensures that american weapon is equipped in and maintain the leading position next century and one of gordian technique that need greatly develop.In the 80's ~ 90 of 20th century, the U.S. carried out twice large-scale adaptive wing study program, be called MAW(Mission Adaptive Wing) and AFW(Active Flexible Wing) plan, MAW adopts mechanical drive system, in the structural materials of surface coverage one deck flexibility of wing, make in the leading edge of a wing and trailing edge control surface part energy smooth transition, eliminate the discontinuous of aerofoil surface, and experimental verification has been carried out on F-111 aircraft, remarkable improvement is obtained in subsonic mode airworthiness of getting off the plane, but due to mechanical drive system too complexity structural weight is significantly increased and cannot apply in practice.
Summary of the invention
The object of the invention is to solve above-mentioned prior art Problems existing, namely.And then a kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material is provided.
The object of the invention is to be achieved through the following technical solutions:
Use a self adaptation trailing edge actuating device for piezoelectric fibre composite material, comprise substrate and piezoelectric fibre composite material, described piezoelectric fibre composite material is pasted onto on the surface of both sides up and down of substrate.Described piezoelectric fibre composite material is that array is pasted onto on substrate, and alite paste used is epoxy resin.Described piezoelectric fibre composite material connects an independently high tension supply separately, and the output area of high tension supply is-500V ~+1500V.
Beneficial effect of the present invention: piezoelectric fibre composite material of the present invention is pasted onto substrate upper and lower surface, the high tension supply that each piezoelectric fibre composite material uses is separate, output voltage does not interfere with each other, therefore the propulsive effort of each piezoelectric fibre composite material output is separate, the distortion of substrate generation variform can be driven, the present invention is installed to alternative conventional rudder face on wing and controls the state of flight of aircraft.Present invention utilizes piezoelectric fibre composite material fast response time, lightweight, be easy to control advantage, the distortion of the variform of substrate generation continuous and derivable can be driven.Structure of the present invention is simple, reasonable in design, stable.
Accompanying drawing explanation
Fig. 1 is the structural representation that the present invention uses the self adaptation trailing edge actuating device of piezoelectric fibre composite material;
Fig. 2 is the A-A cutaway view of Fig. 1;
Fig. 3 to Fig. 5 is design sketch of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail: the present embodiment is implemented under premised on technical solution of the present invention, gives detailed embodiment, but protection scope of the present invention is not limited to following embodiment.
As depicted in figs. 1 and 2, a kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material involved by this example, comprise substrate 1 and piezoelectric fibre composite material 2, described piezoelectric fibre composite material 2 is pasted onto on the surface of both sides up and down of substrate 1.
The size of substrate 1 and the quantity of piezoelectric fibre composite material 2 all need to select according to actual needs, with satisfied design and actual needs.
Described piezoelectric fibre composite material 2 is pasted on substrate 1 in array, and alite paste used is epoxy resin.
The model of piezoelectric fibre composite material 2 is selected and is arranged that quantity is selected, according to actual needs with satisfied design and actual needs.
Described piezoelectric fibre composite material 2 connects an independently high tension supply separately, the output area of high tension supply is-500V ~+1500V, the high tension supply that each piezoelectric fibre composite material 2 connects is separate, output voltage does not interfere with each other, setting like this, the propulsive effort that each piezoelectric fabric is exported is separate.
As shown in Figure 3, apply unified positive voltage to the piezoelectric fibre composite material 2 being pasted onto substrate 1 upper surface, apply unified negative voltage to the piezoelectric fibre composite material 2 being pasted onto substrate 1 lower surface, substrate is bent downwardly, and degree of crook is by voltage control.
As shown in Figure 4, apply unified negative voltage to the piezoelectric fibre composite material 2 being pasted onto substrate 1 upper surface, apply unified positive voltage to the piezoelectric fibre composite material 2 being pasted onto substrate 1 lower surface, substrate K/UP, degree of crook is by voltage control.
As shown in Figure 5, apply negative voltage to substrate 1 upper surface near the two panels piezoelectric fibre composite material of left end, the two panels piezoelectric fibre composite material near right-hand member applies positive voltage; Apply positive voltage to substrate 1 lower surface near the two panels piezoelectric fibre composite material of left end, the two panels piezoelectric fibre composite material near right-hand member applies negative voltage, and can make substrate generation left end K/UP, the reclinate distortion of right-hand member, deformation extent is by voltage control.
As shown in Fig. 3 ~ Fig. 5, the present invention be arranged on as rudder face on the aerofoil of aircraft left and right, the rudder face controlled on the aerofoil of left and right bends all up or down, can realize the pitch control subsystem of aircraft; The rudder face controlled on the aerofoil of left and right bends one on the other, can realize the roll unloads of aircraft; Control one-sided two ends, rudder face left and right to bend one on the other, the driftage that can realize aircraft controls, and three axles that so can realize aircraft control.
The above; be only the present invention's preferably detailed description of the invention; these detailed description of the invention are all based on the different implementations under general idea of the present invention; and protection scope of the present invention is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (1)
1. one kind is used the self adaptation trailing edge actuating device of piezoelectric fibre composite material, comprise substrate (1) and piezoelectric fibre composite material (2), described piezoelectric fibre composite material (2) is pasted onto on the surface of the both sides up and down of substrate (1), and alite paste used is epoxy resin; Described piezoelectric fibre composite material (2) connects an independently high tension supply separately, and it is characterized in that, described piezoelectric fibre composite material (2) is pasted onto on substrate (1) in array; The output area of described high tension supply is-500V ~+1500V, when applying unified positive voltage to the piezoelectric fibre composite material (2) being pasted onto substrate (1) upper surface, when applying unified negative voltage to the piezoelectric fibre composite material (2) being pasted onto substrate (1) lower surface, substrate (1) is bent downwardly; Or when applying unified negative voltage to the piezoelectric fibre composite material (2) being pasted onto substrate (1) upper surface, when unified positive voltage is applied to the piezoelectric fibre composite material (2) being pasted onto substrate (1) lower surface, substrate (1) K/UP; Or when applying negative voltage to substrate (1) upper surface near the two panels piezoelectric fibre composite material (2) of left end, two panels piezoelectric fibre composite material (2) near right-hand member applies positive voltage, near the two panels piezoelectric fabric composite wood (2) of left end, positive voltage is applied to substrate (1) lower surface, when the two panels piezoelectric fibre composite material (2) of right-hand member applies negative voltage, substrate (1) left end K/UP, right-hand member is bent downwardly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310126929.4A CN103171757B (en) | 2013-04-13 | 2013-04-13 | A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310126929.4A CN103171757B (en) | 2013-04-13 | 2013-04-13 | A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material |
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| Publication Number | Publication Date |
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| CN103171757A CN103171757A (en) | 2013-06-26 |
| CN103171757B true CN103171757B (en) | 2015-07-29 |
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| CN201310126929.4A Expired - Fee Related CN103171757B (en) | 2013-04-13 | 2013-04-13 | A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103387048B (en) * | 2013-07-27 | 2016-01-06 | 哈尔滨工业大学 | The variant flexible trailing edge structure of pneumatic actuation/distortion/carrying integration |
| CN103482060A (en) * | 2013-09-01 | 2014-01-01 | 大连理工大学 | Turbulence device based on piezoelectric bimorph |
| CN105523169B (en) * | 2015-12-28 | 2017-11-03 | 哈尔滨工业大学 | A kind of wing rudder face of Variable-Bend |
| CN105639824B (en) * | 2016-03-28 | 2017-11-28 | 联想(北京)有限公司 | A kind of material and Wearable |
| CN110053760B (en) * | 2019-04-11 | 2021-03-05 | 哈尔滨工业大学（深圳） | Flexible deformable wing |
| CN111232186B (en) * | 2020-02-26 | 2022-12-06 | 大连理工大学 | Variable camber wing of trailing edge of piezoelectricity fiber material driven |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4845357A (en) * | 1988-02-11 | 1989-07-04 | Simmonds Precision Products, Inc. | Method of actuation and flight control |
| US5206806A (en) * | 1989-01-10 | 1993-04-27 | Gerardi Joseph J | Smart skin ice detection and de-icing system |
| EP1090835A1 (en) * | 1999-10-09 | 2001-04-11 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Surface actuator for deforming an elastic plate structure |
| CN101659321A (en) * | 2009-10-12 | 2010-03-03 | 北京航空航天大学 | Inflatable wing with controllable sway trailing edge |
| CN101693467A (en) * | 2009-10-13 | 2010-04-14 | 南京航空航天大学 | Self-adapting morphing trailing edge based on SMA |
| CN102167155A (en) * | 2011-04-01 | 2011-08-31 | 哈尔滨工业大学 | Aircraft with turnable wings |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7036769B2 (en) * | 2003-05-14 | 2006-05-02 | The Regents Of The University Of California | Microstructures using carbon fiber composite honeycomb beams |
-
2013
- 2013-04-13 CN CN201310126929.4A patent/CN103171757B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4845357A (en) * | 1988-02-11 | 1989-07-04 | Simmonds Precision Products, Inc. | Method of actuation and flight control |
| US5206806A (en) * | 1989-01-10 | 1993-04-27 | Gerardi Joseph J | Smart skin ice detection and de-icing system |
| EP1090835A1 (en) * | 1999-10-09 | 2001-04-11 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Surface actuator for deforming an elastic plate structure |
| CN101659321A (en) * | 2009-10-12 | 2010-03-03 | 北京航空航天大学 | Inflatable wing with controllable sway trailing edge |
| CN101693467A (en) * | 2009-10-13 | 2010-04-14 | 南京航空航天大学 | Self-adapting morphing trailing edge based on SMA |
| CN102167155A (en) * | 2011-04-01 | 2011-08-31 | 哈尔滨工业大学 | Aircraft with turnable wings |
Non-Patent Citations (1)
| Title |
|---|
| 压电纤维复合材料铺层用于翼面设计的驱动特性与刚度影响;李敏等;《航空学报》;20100228;第31卷(第2期);418-425 * |
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| CN103171757A (en) | 2013-06-26 |
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